Abstract
The mechanism of impact crater formation in metallic and composite space debris shields has been investigated. Hypervelocity impact tests are carried out using 2 mm thick aluminium (Al 2017), carbon polymide and fiber metal laminate space debris shields in a two-stage light gas gun. A cylindrical projectile made of high-density polyethylene (14 mm dia) at a muzzle speed of ~ 5 km/s is used to create the craters in the debris bumper shields. The metallurgical investigation of the craters revealed the formation of adiabatic shear bands as the primary fracture mechanism in aluminium plates at impact angles of 90°, 51° and 64°. Surface delamination zones caused by the peeling of surface piles surrounding the impact and exit craters are observed in the case of carbon polymide and fibre metal laminate debris shields at normal impact. The emission spectroscopic study revealed intense CN and Al emission lines near the crater zone case of Al 2017 debris shields. The presence of CN essentially signifies the partial degradation of the polyethylene projectile during hypervelocity impact. Based on the CN emission the non-equilibrium temperature near the crater zone is estimated to be ~9000K.
| Original language | English |
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| Publication status | Published - 2001 Dec 1 |
| Event | 39th Aerospace Sciences Meeting and Exhibit 2001 - Reno, NV, United States Duration: 2001 Jan 8 → 2001 Jan 11 |
Other
| Other | 39th Aerospace Sciences Meeting and Exhibit 2001 |
|---|---|
| Country/Territory | United States |
| City | Reno, NV |
| Period | 01/1/8 → 01/1/11 |
ASJC Scopus subject areas
- Space and Planetary Science
- Aerospace Engineering